Emulsion explosives with gas bubbles that are resistant to in-borehole migration or coalescence are disclosed herein. Such emulsions can be sensitized by mechanically-introducing gas bubbles into the emulsion. Resistance to gas bubble migration and coalescence can be achieved by homogenization, without the need for bubble stabilization agents.

Emulsion explosives with gas bubbles that are resistant to in-borehole migration or coalescence are disclosed herein. Such emulsions can be sensitized by mechanically-introducing gas bubbles into the emulsion. Resistance to gas bubble migration and coalescence can be achieved by homogenization, without the need for bubble stabilization agents.

An explosive, in particular a water-in-oil emulsion explosive, comprising a water-based explosive composition and a gas, wherein the gas is infused with two different ranges of sizes of nanobubbles, to provide controlled hotspots for detonation to improve emulsion stability and detonation sensitivity. Into the Nano Bubble tank (31) are fed the pressurised gas in water through valve (26) and also a sample is fed into the Nano Bubble tank (31). This then provides the NanoBubble Input NBIbp1 to be fed by NB Feed Pump (33) into static mixer (51). Also fed to the Static Mixer (51) by matrix pump (41) is the explosives containing PIBSA (Poly-Iso-Butylene Succinic Anhydride) in emulsion form as Emulsion Input EInp1 from Emulsion Matrix truck. The static mixer allows for the gas to be infused into the water-based explosive composition in at least a substantial part in the form of nanobubbles (NB) which then forms a controlled explosive output for use in the blast hole (61) by the bubbles acting as a sensitiser as so called “hot spots” which transfer the energy throughout the explosive charge once initiated. This allows the thermal “hot spot” detonation wave to travel through and carries the explosive to a full and controlled detonation.

The present invention provides a method of stabilizing a nitrate-based explosive through the use of a NOx scavenger. The present invention further provides a blasting agent including ammonium nitrate and a NOx scavenger. The present invention further provides for a method of blasting adapted for use in reactive and/or elevated temperature ground.

A high density, generally recognized as safe, hybrid rocket motor is described, having a density-specific impulse similar to a solid rocket motor, with good performance approaching or equal to a liquid rocket motor. These high density hybrid motors resolve the packaging efficiency/effectiveness problems limiting the application of safe, low cost hybrid motor technology.

A precursor formulation comprising, before curing, a hydroxyl-terminated polybutadiene (HTPB) prepolymer or a hydroxyl-terminated polyether (HTPE) prepolymer, an oxidizer, a dimer fatty diol, and an isocyanate curative. A solid propellant comprising a reaction product of the HTPB prepolymer or HTPE prepolymer, the dimer fatty diol, and the isocyanate curative is also disclosed, as is a rocket motor comprising a case and a solid propellant in the case, the solid propellant comprising the reaction product and an oxidizer. A method of reducing a burn rate of a solid propellant is also disclosed.

A method for making a pyrotechnic composition in accordance with an embodiment of the present technology includes flowing metal powder, polytetrafluoroethylene powder, and binder powder in separate respective feed streams toward an extruder. The binder powder includes adhesive material and polytetrafluoroethylene anticaking material coating the adhesive material. The method further includes interspersing the metal powder, the binder powder, and the fluoropolymer powder to form a mixture. This mixture is then subjected to an extrusion process during which the anticaking material coating the adhesive material is disrupted. This releases the adhesive material to bind together the metal powder and the polytetrafluoroethylene powder in the extrudate. The powder mixture includes no solvent at any time between being formed and being extruded, yet the extrudate is well-mixed and cohesive.

The present invention is to provide an explosive composition comprising at least one explosive and at least one heteroatom compound, the heteroatom compound comprising at least one heteroatom selected from the group consisting of B, P, Si, S, Cr, Sn, Al, Ge, Li, Na, K, Cs, Mg, Ca, Sr, Ba, Ti, Zr, V, Nb, Ta, Mo, W, Mn, Ni, Cu, Ag, Cd, Hg, Ga, In, Tl, As, Sb, Bi, Se, Te, Co, Xe, F, Y, and lanthanoids.

Various embodiments of a vortex hybrid motor are described herein. In some embodiments, the vortex hybrid motor may include a combustion zone defined by a fuel core and/or motor housing. The combustion zone may include an upper zone and a central zone that each contribute to thrust created by the vortex hybrid motor. In some embodiments, an injection port configuration is described that includes a proximal injection port that may be controlled for modulating a delivery of an amount of oxidizer for adjusting an oxidizer-to-fuel ratio. In some embodiments, a fuel core configuration is described that provides radially varying gradients of fuel in order to achieve desired thrust profiles. In some embodiments, the fuel core may include a support structure and/or a proximal end of a nozzle of the vortex hybrid motor may extend into the fuel core.

Various embodiments of a vortex hybrid motor are described herein. In some embodiments, the vortex hybrid motor may include a combustion zone defined by a fuel core and/or motor housing. The combustion zone may include an upper zone and a central zone that each contribute to thrust created by the vortex hybrid motor. In some embodiments, an injection port configuration is described that includes a proximal injection port that may be controlled for modulating a delivery of an amount of oxidizer for adjusting an oxidizer-to-fuel ratio. In some embodiments, a fuel core configuration is described that provides radially varying gradients of fuel in order to achieve desired thrust profiles. In some embodiments, the fuel core may include a support structure and/or a proximal end of a nozzle of the vortex hybrid motor may extend into the fuel core.